CN109540534B - Continuous body emitter and method for blade of aviation engine FOD model - Google Patents
Continuous body emitter and method for blade of aviation engine FOD model Download PDFInfo
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- CN109540534B CN109540534B CN201811463272.XA CN201811463272A CN109540534B CN 109540534 B CN109540534 B CN 109540534B CN 201811463272 A CN201811463272 A CN 201811463272A CN 109540534 B CN109540534 B CN 109540534B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
Abstract
The present invention provides a kind of continuous body emitters and method for blade of aviation engine FOD model, belong to aero-engine foreign object strike vibratory response experimental technique field.The device includes jacking module, the module that feeds intake, transmitting module and test module.The module that feeds intake, transmitting module and the test module is sequentially connected, and is mounted in jacking module；A kind of continuous body emitter for blade of aviation engine FOD model can be realized multiple foreign objects and continuously emit, and can be adjusted to the position for hitting blade；The present invention is suitable for the FOD model test of blade of aviation engine, solves the problems such as existing emitter application method is complicated, is unable to complete more foreign objects continuously hits and can not adjust simulation foreign object strike leaf position.
Description
Technical field
The invention belongs to aero-engine foreign object strike vibratory response experimental technique fields, especially design a kind of for navigating
The continuous body emitter and method of empty engine blade FOD (Foreign Object Damage) model.
Background technique
Blade of aviation engine is the more serious aircraft accident of aircraft by foreign object strike, and by taking bird is hit as an example, the whole world is every
10,000 times or more accidents nearly occur for year, upgrade to " A " class aviation disaster by Federation Aeronautic International.Since the problem belongs to again
Miscellaneous nonlinear scale spaces dynamics problem is related to shock loading, fluid structurecoupling, solid coupling, geometrical non-linearity, material nonlinearity
And Transient Dynamics etc..Current theoretical analysis method can not solve problems at all, therefore experimental study is such asks
Inscribe most effective solution.Since its working environment is complicated, foreign object shape is different and the factors such as engine structure valuableness,
Therefore the selection of model test is of great significance.
The currently used bird impact tests platform launching simulation body in a manner of air bubble mostly, disadvantage is that once
Test can only emit one piece of simulant missile and impingement position is fixed, emitter air-tightness requirement is high, the loading of body is more numerous
It is trivial etc..
Summary of the invention
In view of the problems of the existing technology, the present invention provides a kind of companies for blade of aviation engine FOD model
Continuous body emitter and method, the present invention not only can with the multiple simulant missiles of single emission, also by control motor speed and
The emission rate of friction pulley size Control body can also be realized by increasing the height of emitter to different location blade
Shock.This emitter function more fully, reduces experimental cost, while shortening experimental period than existing methods.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
A kind of continuous body emitter for blade of aviation engine FOD model, the continuous body emitter packet
Include jacking module, the module that feeds intake, transmitting module and test module.The jacking module is used to carry out the firing altitude of gun barrel
It adjusts, the position to hit blade to simulant missile is adjusted, to probe into different impingement positions (height) to blade power
Learn the influence of characteristic；Jacking module includes testing stand pedestal, stepper motor, profile, lifting platform, lead screw, mother lead screw, optical axis, cunning
Block, first shaft coupling, top support plate, worm gear, worm screw, motor bearing seat, V-type band and V belt wheel；The profile is fixed on top
Between portion's support plate and testing stand pedestal, it is used to support all structures；Two are arranged between testing stand pedestal and top support plate
Lead screw and two optical axises, two lead screws or two optical axises are centrosymmetric arrangement；Lifting platform is passed through by lead screw and optical axis, and respectively
It is matched by mother lead screw and sliding block with lead screw and optical axis, it is ensured that can be transported up and down between testing stand pedestal and top support plate
It is dynamic；The stepper motor is fixed on testing stand pedestal by motor bearing seat, and the output shaft of stepper motor passes through first
Axis device is connected with worm screw, carries out the transmitting of power and torque；Worm gear is fixed on a lead screw, is driven by the cooperation with worm screw
Lead screw is rotated；V belt wheel is respectively set on two lead screws, V belt wheel is located at the lower section of worm gear, passes through V-type between two V belt wheels
Band is connected；The rotation of stepper motor both forward and reverse directions is realized former and later two lead screws and is rotated synchronously；And then change the height of lifting platform.
The optical axis is used to guarantee the stability and accuracy of operating elevating platform, in addition uses Worm and worm-wheel gearing
It can guarantee that lifting platform will not decline because of gravity in motor stationary state.
The module that feeds intake includes playing slot bearing plate, playing slot roof supporting, first motor support base, rigid shaft coupling
Device, servo motor, rotating missile slot, aluminum profile, simulant missile and steel pipe；The bullet slot bearing plate and bullet slot roof supporting point
It is not fixed on lifting platform by steel pipe and aluminum profile；Rotating missile slot be set to play slot bearing plate and play slot roof supporting it
Between, servo motor is fixed on by first motor support base and is played on slot roof supporting；Servo motor makes to revolve by positive coupling
Turn bullet slot to be rotated, plays and open up consistent with rotating missile trough aperture dimension open on slot bearing plate and bullet slot roof supporting
Mouthful, when the opening of rotating missile slot just matches with the opening for playing slot roof supporting, simulant missile can all be put into rotation
Turn to play in slot；Meanwhile when the opening for playing slot bearing plate matches with the opening of rotating missile slot, simulant missile is just successively fallen
Into gun barrel.
The transmitting module includes gun barrel, gun barrel fulcrum bearing, steel pipe, driving motor, the second motor supporting base, second
Axis device, driving shaft, driven shaft, active synchronization belt wheel, driven synchronous pulley A, driven synchronous pulley B, driven synchronous pulley C, from
Dynamic synchronous pulley D, driven synchronous pulley E, synchronous belt A, synchronous belt B, synchronous belt C, synchronous belt D, gear wheel-train, gear shaft, tooth
Axle bearing seat, angular contact ball bearing, friction pulley and simulant missile；The gun barrel is fixed on lifting platform by gun barrel fulcrum bearing
On, stack shell two sides open up three windows respectively；Driving motor is fixed on by the second motor bearing seat to be played on slot bearing plate；It is main
Moving axis and driven shaft are set to lifting platform and play between slot bearing plate, are located at gun barrel two sides, wherein the left side setting one of gun barrel
The lower end of root driving shaft and two driven shafts, a driving shaft and two driven shafts is successively arranged active synchronization belt wheel, driven same
Belt wheel A, driven synchronous pulley B are walked, upper end is arranged friction pulley, and friction pulley is corresponding with the window on gun barrel stack shell；Big gun
Three driven shafts of right side setting corresponding with left side of cylinder, the upper end of three driven shafts are arranged friction pulley, and lower end is successively arranged
Driven synchronous pulley C, driven synchronous pulley D and driven pulley E；The upper end of driving shaft passes through second shaft coupling and driving motor phase
Even, the upper and lower ends of the lower end of driving shaft and all driven shafts pass through angular contact ball bearing respectively with lifting platform, play slot branch
Bottom plate is held to be connected；Divide between active synchronization belt wheel and driven synchronous pulley A, between driven synchronous pulley A and driven synchronous pulley B
It An Zhuan not synchronous belt A, synchronous belt B；Between driven synchronous pulley C and driven synchronous pulley D, driven synchronous pulley D and driven belt
It takes turns and synchronous belt C, synchronous belt D is installed between E；Driving shaft and the setting gear shaft fulcrum bearing between actively axisymmetric driven shaft,
Two rooted tooth wheel shafts are set between gear shaft fulcrum bearing and lifting platform, and two rooted tooth wheel shafts and driving shaft are located at same straight line；Actively
It is arranged gear, structure between four gears respectively at the sustained height of axis, two rooted tooth wheel shafts and the axisymmetric driven shaft of active
At gear wheel-train；
Driving motor drives driving shaft rotation through second shaft coupling, and power and torque are transmitted to actively same by driving shaft by key
It walks on belt wheel, the transmitting of synchronized band A and synchronous belt B, driven synchronous pulley A and driven synchronous pulley B start to be rotated；Into
And by the transmission of gear wheel-train, driving shaft is transferred the motion to again on the driven shaft where driven synchronous pulley C, passes through synchronization
Drive with C and synchronous belt D, driven synchronous pulley D and driven pulley E start to be rotated, and all driven synchronous pulleys turn
The dynamic rotation that can drive the driven shaft where it；Power and torque can be transmitted to friction by key by final driving shaft and driven shaft
On wheel；Because all consistent and active synchronization belt wheel is also all consistent with the size of driven synchronous pulley C for the gear in gear wheel-train,
Therefore active synchronization belt wheel and the rotation speed of driven synchronous pulley C are consistent, the rotation speed of place axis is also consistent；It is driven same
Step belt wheel A corresponds to each other with driven synchronous pulley D, size is consistent；Driven synchronous pulley B and driven synchronous pulley E correspond to each other,
Size is consistent；So the friction wheel from rotation speed of gun tube two sides opposite position is consistent；It is again because active synchronization belt wheel, driven same
The size walked between belt wheel and driven synchronous pulley B has difference, so coaxially upper the obtained speed of friction pulley is not also different
It causes, simulant missile accelerates by the classification of friction pulley, and simulant missile is projected.By adjust driving motor revolving speed it is fast
Slowly, the speed projected to simulant missile controls.
The test module includes feed intake counter, optoelectronic switch and travel switch；The counter setting that feeds intake
In the aperture position of rotating missile slot, the quantity that simulant missile is fallen is monitored；Optoelectronic switch is set to launching for gun barrel
Mouth position, the speed projected to simulant missile are monitored；Travel switch is set to the high-low limit position that sliding block can be run, right
The height of lifting platform is controlled.
The number of teeth of three ipsilateral synchronous pulleys is different, and bigger closer to the number of teeth of rotating missile slot, realizes that classification accelerates
Function, and simulant missile is avoided to be destroyed by frictional force；The number of teeth of the synchronous pulley of heteropleural relative position is identical, guarantees two sides pair
It answers the revolving speed of friction pulley identical, the direction of motion of simulant missile is avoided to deviate.
A kind of continuous body launching technique for blade of aviation engine FOD model, steps are as follows:
Step 1: height adjustment is carried out to emitter for different impingement positions；
The rotation of lead screw is driven by stepper motor, thus move up and down lifting platform under the drive of mother lead screw,
The cooperation of optical axis and sliding block guarantees the stability and accuracy of operating elevating platform, in addition can be protected using Worm and worm-wheel gearing
Card lifting platform in stepper motor stationary state will not decline because of gravity.
Step 2: multiple simulant missiles are transported in transmitting module simultaneously；
By controlling the fine rotational of servo motor, the counting slot that guarantee magazine opening accurately rests on rotating missile slot is opened
On mouth, so that simulant missile is directly entered in rotating missile slot.After simulant missile entirely falls in rotating missile slot in magazine, servo electricity
Machine continues to rotate, and when the notch at the outlet of rotating missile slot and gun barrel coincides, transmitting module can be to multiple simulations
Body is emitted.
Step 3: multiple simulant missiles are emitted；
Driving motor drives spindle rotation by second shaft coupling, passes through ipsilateral synchronous belt and driven synchronous belt
Wheel, to drive ipsilateral friction pulley to carry out equidirectional rotation.Meanwhile being made up of the straight-tooth external gear by four identical numbers of teeth
Gear wheel-train drives the driven shaft of driving shaft heteropleural to be reversely rotated, fall to simulant missile in gun barrel and friction pulley it
Between generate frictional force, this frictional force generates the external force to direction blade by itself rotation of friction pulley, and then carries out acceleration fortune
It is dynamic, directive fan blade.
The invention has the following advantages:
The present invention is a kind of continuous body emitter for blade of aviation engine FOD model, using completely new
Design scheme, solve existing emitter it is bulky, it is complicated for operation, be unable to complete continuous several times hit, impingement position can not
The problems such as tune.Due to simulating the operating condition that foreign object is continuously hit using more body emitters, closer to actual conditions, pass through friction
Wheel controls the stroke speed of body to realize influence of the friction speed foreign object for blade, and can be by increasing emitter
The shock to different location blade is realized in position.Simulation for foreign object strike can both have been realized by the use of rotating missile slot
Single foreign object and can complete the test that continuous multiple foreign objects hit blade for the impact test of blade.
Detailed description of the invention
Fig. 1 is that a kind of continuous body emitter overall structure for blade of aviation engine FOD model of the present invention is shown
It is intended to；
Fig. 2 is that a kind of continuous body emitter jacking module for blade of aviation engine FOD model of the present invention is shown
It is intended to；
Fig. 3 is that a kind of continuous body emitter for blade of aviation engine FOD model of the present invention module that feeds intake is shown
It is intended to；
Fig. 4 is a kind of continuous body emitter transmitting module knot for blade of aviation engine FOD model of the present invention
Structure schematic diagram；
In figure: 1 jacking module；2 feed intake module；3 transmitting modules；4 test modules；101 testing stand pedestals；102 steppings electricity
Machine；103 profiles；104 lifting platforms；105 lead screws；106 mother lead screws；107 optical axises；108 sliding blocks；109 first shaft couplings；110 tops
Support plate；111 worm gears；112 worm screws；113 motor bearing seats；114V type band；115V belt wheel；201 play slot bearing plate；202 bullets
Slot roof supporting；203 first motor support bases；204 positive couplings；205 servo motors；206 rotating missile slots；207 aluminum profiles；
208 simulant missiles；301 gun barrels；302 gun barrel fulcrum bearings；303 steel pipes；304 driving motors；305 second motor supporting bases；306
Two shaft couplings；307 driving shafts；308 driven shafts；309 active synchronization belt wheels；310 driven synchronous pulley A；311 driven synchronous pulleys
B；312 driven synchronous pulley C；313 driven synchronous pulley D；314 driven synchronous pulley E；315 synchronous belt A；316 synchronous belt B；
317 synchronous belt C；318 synchronous belt D；319 gear wheel-trains；320 gear shafts；321 gear shaft fulcrum bearings；322 angular contact ball bearings；
323 friction pulleys；324 motor support plates.
Specific embodiment
With reference to the accompanying drawing and technical solution, a specific embodiment of the invention is further illustrated.
As shown in Figure 1, a kind of blade of aviation engine FOD rig for model test overall structure of the present invention, including top
Rising mould block 1, transmitting module 2, the module that feeds intake 3 and test module 4；Test module 4 with to jacking module 1, transmitting module 2, throw
Relevant data are recorded and are detected in material module 3.
As shown in Fig. 2, the jacking module 1 is used to that the firing altitude of gun barrel 301 to be adjusted, to simulant missile
The position of 208 shock blades is adjusted, to probe into influence of the different impingement positions (height) to blade dynamics characteristic；Top
Rising mould block 1 includes testing stand pedestal 101, stepper motor 102, profile 103, lifting platform 104, lead screw 105, mother lead screw 106, optical axis
107, sliding block 108, first shaft coupling 109, top support plate 110, worm gear 111, worm screw 112, motor bearing seat 113, V-type band
114 and V belt wheel 115；The profile 103 is fixed between top support plate 110 and testing stand pedestal 101, is used to support institute
There is structure；Two lead screws 105 and two optical axises 107, two lead screws are set between testing stand pedestal 101 and top support plate 110
105 or two optical axises 107 be centrosymmetric arrangement；Lifting platform 104 is passed through by lead screw 105 and optical axis 107, and passes through lead screw respectively
Mother 106 and sliding block 108 are matched with lead screw 105 and optical axis 107, it is ensured that can testing stand pedestal 101 and top support plate 110 it
Between move up and down；The stepper motor 102 is fixed on testing stand pedestal 101 by motor bearing seat 113, stepper motor
102 output shaft is connected by first shaft coupling 109 with worm screw 112, and the transmitting of power and torque is carried out；Worm gear 111 is fixed on
On a piece lead screw 105, lead screw 105 is driven to be rotated by the cooperation with worm screw 111；V band is respectively set on two lead screws 105
Wheel 115, V belt wheel 115 is located at the lower section of worm gear 112, is connected between two V belt wheels 115 by V-type band 114；Stepper motor 102
Both forward and reverse directions rotation is realized former and later two lead screws 105 and is rotated synchronously；And then change the height of lifting platform 104.
The optical axis 107 is used to guarantee the stability and accuracy that lifting platform 104 is run, in addition be passed using worm and gear
Motivation structure can guarantee that lifting platform will not decline because of gravity in motor stationary state.
As shown in figure 3, the module 2 that feeds intake includes playing slot bearing plate 201, playing slot roof supporting 202, first motor
Support base 203, positive coupling 204, servo motor 205, rotating missile slot 206, aluminum profile 207, simulant missile 208 and steel pipe
303；The bullet slot bearing plate 201 and bullet slot roof supporting 202 is fixed on liter by steel pipe 303 and aluminum profile 207 respectively
It drops on platform 104；Rotating missile slot 206, which is set to, to be played slot bearing plate 201 and plays between slot roof supporting 202, and servo motor 205 is logical
First motor support base 203 is crossed to be fixed on bullet slot roof supporting 202；Servo motor 205 makes to rotate by positive coupling 204
It plays slot 206 to be rotated, plays and opened up and 206 opening size of rotating missile slot on slot bearing plate 201 and bullet slot roof supporting 202
Consistent opening, when the opening of rotating missile slot 206 just matches with the opening for playing slot roof supporting 202, simulant missile
208 can all be put into rotating missile slot 206；Meanwhile when the bullet opening of slot bearing plate 201 and opening for rotating missile slot 206
When mouth matches, simulant missile 208 is just successively fallen in gun barrel 301.
As shown in figure 4, the transmitting module 3 includes gun barrel 301, gun barrel fulcrum bearing 302, steel pipe 303, driving motor
304, the second motor supporting base 305, second shaft coupling 306, driving shaft 307, driven shaft 308, active synchronization belt wheel 309, driven
Synchronous pulley A310, driven synchronous pulley B311, driven synchronous pulley C312, driven synchronous pulley D313, driven synchronous pulley
E314, synchronous belt A315, synchronous belt B316, synchronous belt C317, synchronous belt D318, gear wheel-train 319, gear shaft 320, gear shaft
Fulcrum bearing 321, angular contact ball bearing 322, friction pulley 323 and simulant missile 208；The gun barrel 301 passes through gun barrel fulcrum bearing
302 are fixed on lifting platform 104, and stack shell two sides open up three windows respectively；Driving motor 304 passes through the second motor bearing seat
305 are fixed on bullet slot bearing plate 201；Driving shaft 307 and driven shaft 308 are set to lifting platform 104 and play slot bearing plate
Between 201, it is located at 301 two sides of gun barrel, wherein a left side piece driving shaft 307 of setting for gun barrel 301 and two driven shafts 308, one
The lower end of root driving shaft 307 and two driven shafts 308 is successively arranged active synchronization belt wheel 309, driven synchronous pulley A310, driven
Synchronous pulley B311, upper end is arranged friction pulley 323, and friction pulley 323 is corresponding with the window on 301 stack shell of gun barrel；Big gun
Three driven shafts 308 of right side setting corresponding with left side of cylinder 301, the upper end of three driven shafts 308 are arranged friction pulley 323,
Lower end is successively arranged driven synchronous pulley C312, driven synchronous pulley D313 and driven pulley E314；The upper end of driving shaft 307 is logical
It crosses second shaft coupling 306 to be connected with driving motor 304, the upper and lower ends of the lower end of driving shaft 307 and all driven shafts 308 are equal
It is connected respectively with lifting platform 104, bullet slot bearing plate 201 by angular contact ball bearing 322；Active synchronization belt wheel 309 with it is driven
Synchronous belt A315, same is installed respectively between synchronous pulley A310, between driven synchronous pulley A310 and driven synchronous pulley B311
Step band B316；Between driven synchronous pulley C312 and driven synchronous pulley D313, driven synchronous pulley D313 and driven pulley
Synchronous belt C317, synchronous belt D318 are installed between E314；It driving shaft 307 and is set between the symmetrical driven shaft 308 of driving shaft 307
Gear shaft fulcrum bearing 321 is set, two rooted tooth wheel shafts 320, two rooted tooth wheel shafts are set between gear shaft fulcrum bearing 321 and lifting platform 104
320 are located at same straight line with driving shaft 307；Driving shaft 307, two rooted tooth wheel shafts 320 and the symmetrical driven shaft of driving shaft 307
Gear is arranged at 308 sustained height respectively, four gears constitute gear wheel-train 319 each other；
Driving motor 304 drives driving shaft 307 to rotate through second shaft coupling 306, and driving shaft 307 passes through key for power and torque
It is transmitted in active synchronization belt wheel 309, the transmitting of synchronized band A315 and synchronous belt B316, driven synchronous pulley A310 and driven
Synchronous pulley B311 starts to be rotated；And then by the transmission of gear wheel-train 319, driving shaft 307 transfer the motion to again from
On driven shaft 308 where dynamic synchronous pulley C312, by the drive of synchronous belt C317 and synchronous belt D318, driven synchronous pulley
D313 and driven pulley E314 start to be rotated, and the rotation of all driven synchronous pulleys can drive the driven shaft where it
Rotation；Power and torque can be transmitted on friction pulley 323 by final driving shaft 307 and driven shaft 308 by key；Because of gear wheel-train
All consistent and active synchronization belt wheel 309 is also all consistent with the size of driven synchronous pulley C312 for gear in 319, therefore actively
Synchronous pulley 309 is consistent with the rotation speed of driven synchronous pulley C312, and the rotation speed of place axis is also consistent；It is driven same
Step belt wheel A310 corresponds to each other with driven synchronous pulley D313, size is consistent；Driven synchronous pulley B311 and driven synchronous pulley
E314 corresponds to each other, and size is consistent；So corresponding 323 rotation speed of friction pulley in 301 two sides of gun tube is consistent；Again because actively
Size between synchronous pulley 309, driven synchronous pulley and driven synchronous pulley B311 has difference, so not coaxially upper friction
Wheel 323 obtained speed be also it is inconsistent, simulant missile 208 process friction pulley 323 classification acceleration, simulant missile is penetrated
Out.By adjusting the speed of the revolving speed of driving motor 304, the speed projected to simulant missile 208 is controlled.
The test module 4 includes feed intake counter, optoelectronic switch and travel switch；The counter setting that feeds intake
In the aperture position of rotating missile slot 206, the quantity fallen to simulant missile 208 is monitored；Optoelectronic switch is set to gun barrel 301
Transmitting outlet port, to simulant missile project speed be monitored；Travel switch be set to that sliding block 108 can run up and down
Extreme position controls the height of lifting platform 104.
A kind of continuous body launching technique for blade of aviation engine FOD model, comprising the following steps:
Step 1: height adjustment is carried out to emitter for different impingement positions；Silk is driven by stepper motor 102
The rotation of thick stick 105, so that lifting platform 104 be made to move up and down under the drive of mother lead screw 106, optical axis 107 and sliding block 108
Cooperation guarantees the stability and accuracy that lifting platform 104 is run, and in addition can be guaranteed using Worm and worm-wheel gearing in motor
Lifting platform 104 will not decline because of gravity when stationary state.
Step 2: multiple simulant missiles 208 are transported in transmitting module 3 simultaneously；By the essence for controlling driving motor 304
Really rotation guarantees that magazine opening accurately rests on and counts on channel opening, counts in slot so that simulant missile 208 is directly entered.
After simulant missile 208 entirely falls in counting slot in magazine, driving motor 304 continues to rotate, slot outlet to be counted and big gun
When notch at cylinder 301 coincides, transmitting module 3 can emit multiple simulant missiles 208.
Step 3: multiple simulant missiles 208 are emitted；By controlling the rotation of driving motor 304, and pass through gear
It is fallen in gun barrel 301 between simulant missile 208 and friction pulley 323 with the transmitting of belt wheel to drive the rotation of friction pulley 323
Certain frictional force is generated, this frictional force is generated opposite by itself rotation of friction pulley 323 between simulant missile 208
Frictional force generates the external force to direction blade, and then carries out acceleration movement, directive fan blade.Driving motor 304 passes through the
Two shaft couplings 306 drive driving shaft 307 to rotate, and are driving ipsilateral friction pulley equidirectional by ipsilateral synchronous belt and Toothed belt pulley
Rotation.In addition, the straight-tooth external gear train 319 by four identical numbers of teeth reversely revolves the driven shaft 308 of 307 heteropleural of driving shaft
Turn, three ipsilateral synchronous pulley numbers of teeth are different, and bigger closer to the rotation magazine number of teeth, realize the function that classification accelerates, protection
Simulant missile 208 and friction pulley 323 are destroyed by frictional force also has acceleration function；The number of teeth of heteropleural Toothed belt pulley with it is ipsilateral right
It answers the number of teeth of Toothed belt pulley identical, guarantees that two sides correspond to the revolving speed difference of friction pulley, avoid the direction of motion of simulant missile 208
Deviate.
Claims (3)
1. a kind of continuous body emitter for blade of aviation engine FOD model, which is characterized in that the continuous body hair
Injection device includes jacking module (1), the module that feeds intake (2), transmitting module (3) and test module (4)；
The jacking module (1) hits leaf for the firing altitude of gun barrel (301) to be adjusted, to simulant missile (208)
The position of piece is adjusted, to probe into influence of the different impingement positions to blade dynamics characteristic；Jacking module (1) includes examination
Test platform pedestal (101), stepper motor (102), profile (103), lifting platform (104), lead screw (105), mother lead screw (106), optical axis
(107), sliding block (108), first shaft coupling (109), top support plate (110), worm gear (111), worm screw (112), motor bearing
Seat (113), V-type band (114) and V belt wheel (115)；The profile (103) is fixed on top support plate (110) and testing stand bottom
Between seat (101), it is used to support all structures；Two lead screws are set between testing stand pedestal (101) and top support plate (110)
(105) He Lianggen optical axis (107), two lead screws (105) or two optical axises (107) are centrosymmetric arrangement；Lifting platform (104) quilt
Lead screw (105) and optical axis (107) pass through, and pass through thick stick mother 106 and sliding block (108) and lead screw (105) and optical axis (107) phase respectively
Cooperation, it is ensured that can move up and down between testing stand pedestal (101) and top support plate (110)；The stepper motor (102)
It is fixed on testing stand pedestal (101) by motor bearing seat (113), the output shaft of stepper motor (102) passes through the first shaft coupling
Device (109) is connected with worm screw (112), carries out the transmitting of power and torque；Worm gear (111) is fixed on a lead screw (105), is led to
It crosses and drives lead screw (105) to be rotated with the cooperation of worm screw (112)；V belt wheel (115), V is respectively set on two lead screws (105)
Belt wheel (115) is located at the lower section of worm gear (111), is connected between two V belt wheels (115) by V-type band (114)；Stepper motor
(102) both forward and reverse directions rotate, and realize former and later two lead screws (105) and rotate synchronously；And then change the height of lifting platform (104),
Realize the purpose hit the blade of different height；
The module that feeds intake (2) includes playing slot bearing plate (201), playing slot roof supporting (202), first motor support base
(203), positive coupling (204), servo motor (205), rotating missile slot (206), aluminum profile (207), simulant missile (208) and
Steel pipe (303)；The bullet slot bearing plate (201) and bullet slot roof supporting (202) passes through steel pipe (303) and aluminum profile respectively
(207) it is fixed on lifting platform (104)；Rotating missile slot (206), which is set to, plays slot bearing plate (201) and bullet slot roof supporting
(202) between, servo motor (205) is fixed on by first motor support base (203) and is played on slot roof supporting (202)；Servo
Motor (205) rotates rotating missile slot (206) by positive coupling (204), plays slot bearing plate (201) and plays slot branch
Support plate opens up the opening consistent with rotating missile slot (206) opening size on (202), when the opening of rotating missile slot (206)
When just matching with the opening for playing slot roof supporting (202), simulant missile (208) can all be put into rotating missile slot
(206) in；Meanwhile when the opening for playing slot bearing plate (201) matches with the opening of rotating missile slot (206), simulant missile
(208) it just successively falls in gun barrel (301)；
The transmitting module (3) includes gun barrel (301), gun barrel fulcrum bearing (302), driving motor (304), the second motor support
Seat (305), second shaft coupling (306), driving shaft (307), driven shaft (308), active synchronization belt wheel (309), driven synchronous belt
Take turns A (310), driven synchronous pulley B (311), driven synchronous pulley C (312), driven synchronous pulley D (313), driven synchronous belt
Take turns E (314), synchronous belt A (315), synchronous belt B (316), synchronous belt C (317), synchronous belt D (318), gear wheel-train (319), tooth
Wheel shaft (320), gear shaft fulcrum bearing (321), angular contact ball bearing (322), friction pulley (323) and simulant missile (208)；It is described
Gun barrel (301) be fixed on lifting platform (104) by gun barrel fulcrum bearing (302), stack shell two sides open up three windows respectively；It drives
Dynamic motor (304) are fixed on by the second motor supporting base (305) to be played on slot bearing plate (201)；Driving shaft (307) and driven
Axis (308) is set to lifting platform (104) and plays between slot bearing plate (201), is located at gun barrel (301) two sides, wherein gun barrel
(301) driving shaft (307) He Lianggen driven shaft (308), driving shaft (307) He Lianggen driven shaft is arranged in left side
(308) lower end is successively arranged active synchronization belt wheel (309), driven synchronous pulley A (310), driven synchronous pulley B (311), on
End is arranged friction pulley (323), and friction pulley (323) is corresponding with the window on gun barrel (301) stack shell；Gun barrel (301)
Three driven shafts (308) of right side setting corresponding with left side, the upper end of three driven shafts (308) are arranged friction pulley (323), under
End is successively arranged driven synchronous pulley C (312), driven synchronous pulley D (313) and driven synchronous pulley E (314)；Driving shaft
(307) upper end is connected by second shaft coupling (306) with driving motor (304), and the lower end of driving shaft (307) passes through angular contact
Ball bearing (322) is connect with lifting platform (104)；The upper and lower ends of all driven shafts (308) pass through angular contact ball bearing (322)
It is connected respectively with bullet slot bearing plate (201), lifting platform (104)；Active synchronization belt wheel (309) and driven synchronous pulley A (310)
Between, between driven synchronous pulley A (310) and driven synchronous pulley B (311) synchronous belt A (315), synchronous belt B are installed respectively
(316)；Between driven synchronous pulley C (312) and driven synchronous pulley D (313), driven synchronous pulley D (313) with it is driven synchronous
Synchronous belt C (317), synchronous belt D (318) are installed between belt wheel E (314)；Driving shaft (307) and symmetrical with driving shaft (307)
Gear shaft fulcrum bearing (321) are set between driven shaft (308), are arranged two between gear shaft fulcrum bearing (321) and lifting platform (104)
Rooted tooth wheel shaft (320), two rooted tooth wheel shafts (320) and driving shaft (307) are located at same straight line；Driving shaft (307), two rooted tooth wheels
Axis (320), be arranged gear at the sustained height of driving shaft (307) symmetrical driven shaft (308) respectively, four gears each other it
Between constitute gear wheel-train (319)；
The test module (4) includes feed intake counter, optoelectronic switch and travel switch；The counter that feeds intake is set to
The aperture position of rotating missile slot (206), the quantity fallen to simulant missile (208) are monitored；Optoelectronic switch is set to gun barrel
(301) transmitting outlet port, the speed projected to simulant missile are monitored；Travel switch is set to sliding block (108) and can transport
Capable high-low limit position controls the height of lifting platform (104).
2. a kind of continuous body emitter for blade of aviation engine FOD model according to claim 1, special
Sign is that the number of teeth of three ipsilateral synchronous pulleys is different and bigger closer to the number of teeth of rotating missile slot (206), realizes classification
The function of acceleration, and simulant missile (208) is avoided to be destroyed by frictional force；The number of teeth of the synchronous pulley of heteropleural relative position is identical,
The revolving speed that guarantee two sides correspond to friction pulley (323) is identical, and the direction of motion of simulant missile (208) is avoided to deviate.
3. emitting dress using a kind of any continuous body for blade of aviation engine FOD model of claims 1 or 2
The launching technique set, which is characterized in that steps are as follows:
Step 1: height adjustment is carried out to emitter for different impingement positions；
The rotation that lead screw (105) are driven by stepper motor (102), to make lifting platform (104) in the drive of mother lead screw (106)
Under move up and down, the cooperation of optical axis (107) and sliding block (108) guarantees the stability and accuracy of lifting platform (104) operation,
In addition it can guarantee that lifting platform (104) will not be because of weight in stepper motor (102) stationary state using Worm and worm-wheel gearing
Power decline；
Step 2: multiple simulant missiles (208) are transported in transmitting module (3) simultaneously；
By controlling the fine rotational of servo motor (205), guarantee that magazine opening accurately rests on the meter of rotating missile slot (206)
On number channel opening, so that simulant missile (208) is directly entered in rotating missile slot (206)；When simulant missile (208) is whole in magazine
After falling into rotating missile slot (206), servo motor (205) continues to rotate, outlet and gun barrel to rotating missile slot (206)
(301) when the notch at coincides, transmitting module (3) can emit multiple simulant missiles (208)；
Step 3: multiple simulant missiles (208) are emitted；
Driving motor (304) drives driving shaft (307) rotation by second shaft coupling (306), by ipsilateral synchronous belt and
Driven synchronous pulley, to drive ipsilateral friction pulley (323) to carry out equidirectional rotation；Meanwhile by by four identical numbers of teeth
The gear wheel-train (319) of straight-tooth external gear composition, drives the driven shaft (308) of driving shaft (307) heteropleural to be reversely rotated, falls
Frictional force is generated between the simulant missile (208) fallen in gun barrel (301) and friction pulley (323), this frictional force passes through friction pulley
(323) itself rotation generates the external force to direction blade, and then carries out acceleration movement, directive fan blade.
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| CN201811463272.XA CN109540534B (en) | 2018-12-03 | 2018-12-03 | Continuous body emitter and method for blade of aviation engine FOD model |
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| CN111504812B (en) * | 2020-04-27 | 2023-04-11 | 山西采薇集能科技有限公司 | Automatic continuous uploading mechanism for flying piece launching |
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